专利快速检索-快速检索全球专利，免费商用专利数据库-IPRDB

51. 发明申请

US20140224926A1 SYSTEMS AND METHODS FOR CONTROLLING A MAGNITUDE OF A SONIC BOOM 有权
标题翻译：用于控制SONIC BOOM磁头的系统和方法
公开(公告)号：US20140224926A1
公开(公告)日：2014-08-14
申请号：US14176865
申请日：2014-02-10
申请人： Gulfstream Aerospace Corporation
发明人： Donald Freund
IPC分类号： B64C23/00 , B64C3/38 , B64C3/42 , B64C30/00
CPC分类号： B64C23/00 , B64C3/185 , B64C3/20 , B64C3/38 , B64C3/42 , B64C9/00 , B64C17/10 , B64C30/00 , B64D37/00 , Y02T50/14 , Y02T50/44
摘要： A system for controlling a magnitude of a sonic boom includes a first sensor configured to detect a first condition of the supersonic aircraft. The system further includes a pair of wings configured to move fore and aft. The system further includes a processor communicatively coupled with the sensor and operatively coupled with the pair of wings. The processor is configured to (1) receive a first information from the first sensor indicative of the first condition, (2) calculate a lift distribution of the supersonic aircraft based on the first information, (3) determine an existence of a deviation of the lift distribution from a desired lift distribution based on the flight condition, and (4) control the pair of wings to move to redistribute the lift in a manner that more closely conforms to the desired lift distribution. The magnitude of the sonic boom is reduced when the deviation is reduced.
摘要翻译：用于控制声波起重臂的大小的系统包括被配置为检测超音速飞行器的第一状态的第一传感器。该系统还包括一对构造成前后移动的翼。所述系统还包括处理器，其与所述传感器通信地耦合并且与所述一对机翼可操作地耦合。处理器被配置为（1）从第一传感器接收指示第一条件的第一信息，（2）基于第一信息计算超音速飞机的升力分布，（3）确定存在基于飞行条件从所需的升力分布提升分配，以及（4）控制所述一对翼移动以以更符合期望的升力分布的方式重新分配升力。当偏差减小时，声音臂的大小减小。

52. 发明申请

US20140151498A1 QUIET LANDING GEAR DOOR 有权
标题翻译： QUIET登陆齿轮门
公开(公告)号：US20140151498A1
公开(公告)日：2014-06-05
申请号：US13689766
申请日：2012-11-30
申请人： Robin B. Langtry , Drew A. Wetzel
发明人： Robin B. Langtry , Drew A. Wetzel
IPC分类号： B64C23/00 , B64C25/16
CPC分类号： B64C25/001 , B64C23/005 , B64C25/16 , B64C2025/003
摘要： A quiet landing gear door and methods are presented. A landing gear door comprises a trailing edge and a leading edge and is operable to deploy to a landing gear door deployed position. A door flap comprises the trailing edge and is hinged to the landing gear door. The door flap deflects toward a landing gear strut to a door flap deployed position in response to deployment of the landing gear door. A leading edge section comprises the leading edge and is coupled to the door flap. The leading edge section deflects toward the landing gear strut to a leading edge deployed position in response to deployment of the landing gear door.
摘要翻译：提出了一个安静的起落架门和方法。起落架门包括后缘和前缘，并且可操作以部署到起落架门展开位置。门挡板包括后缘并铰接到起落架门。响应于起落架门的展开，门挡板朝着起落架支柱偏转到门翼展开位置。前缘部分包括前缘并联接到门瓣。引导边缘部分响应于起落架门的展开而朝起落架支柱偏转到前缘展开位置。

53. 发明授权

US08695915B1 Flap side edge liners for airframe noise reduction 有权
标题翻译：襟翼侧边缘用于机身降噪
公开(公告)号：US08695915B1
公开(公告)日：2014-04-15
申请号：US13417347
申请日：2012-03-12
申请人： Michael G. Jones , Mehdi R. Khorrami , Meelan M. Choudhari , Brian M. Howerton
发明人： Michael G. Jones , Mehdi R. Khorrami , Meelan M. Choudhari , Brian M. Howerton
IPC分类号： B64C1/40 , B64C23/00
CPC分类号： B64C1/40 , B64C9/18 , B64C21/10 , B64C23/005 , B64C2025/003 , B64C2220/00 , B64C2230/14 , B64C2230/22 , B64C2230/24 , Y02T50/166 , Y02T50/32
摘要： One or more acoustic liners comprising internal chambers or passageways that absorb energy from a noise source on the aircraft are disclosed. The acoustic liners may be positioned at the ends of flaps of an aircraft wing to provide broadband noise absorption and/or dampen the noise producing unsteady flow features, and to reduce the amount of noise generated due to unsteady flow at the inboard and/or outboard end edges of a flap.
摘要翻译：公开了一种或多种声学衬垫，其包括从飞机上的噪声源吸收能量的内部腔室或通道。声学衬垫可以定位在飞机机翼的翼片的端部，以提供宽带噪声吸收和/或抑制产生不稳定流动特征的噪声，并且减少由于内侧和/或外侧的不稳定流动而产生的噪声量翼片的末端边缘。

54. 发明授权

US08628040B2 Aircraft configuration 有权
标题翻译：飞机配置
公开(公告)号：US08628040B2
公开(公告)日：2014-01-14
申请号：US13093596
申请日：2011-04-25
申请人： Matthew D. Moore , Kelly L. Boren , Edward C. Marques , Justin Lan
发明人： Matthew D. Moore , Kelly L. Boren , Edward C. Marques , Justin Lan
IPC分类号： B64C1/40 , B64C23/00
CPC分类号： B64C5/08 , B64C39/12 , B64D27/20
摘要： An aircraft configuration that may reduce the level of roaring jet exhaust noise, infrared radiation, sonic boom, or combination thereof directed towards the ground from an aircraft in flight. The aircraft's nacelles are mounted to the aircraft higher than the wings, with substantially vertical stabilizers outboard of the outermost engine. Noise shifting means are provided such as, for each nacelle, primary chevrons at the core nozzle, secondary chevrons at the fan nozzle, a partial bypass mixer, a long duct full flow mixer, or a combination thereof to provide a shift in spectrum distribution of jet exhaust noise from lower to higher frequency. Variable geometry chevrons may be used with increased immersion to provide such a shift just during noise-restricted portions of an aircraft flight profile. The aircraft aerodynamic structural surfaces serve as noise shielding barriers that more effectively block or redirect the frequency shifted noise up and away from communities.
摘要翻译：一种飞行器配置，其可以降低来自飞行中的飞行器的朝向地面的咆哮的喷气排气噪声，红外辐射，声波起伏或其组合的水平。飞机的发动机舱安装在飞机高于机翼的位置，在最外面的发动机外侧具有大致垂直的稳定器。提供噪声移动装置，例如，对于每个机舱，在核心喷嘴处的主要人字形，在风扇喷嘴处的副人字形，部分旁路混合器，长管道全流量混合器或其组合以提供频谱分布的偏移喷气排气噪声从低频到高频。可变几何人字形可以与增加的浸入使用，以在飞机飞行剖面的噪声限制部分期间提供这种移动。飞机空气动力学结构表面用作噪声屏蔽屏障，可以更有效地阻挡或重定向频率偏移的噪声向上和远离社区。

55. 发明授权

US08596568B2 Exhaust silencer with baffles 有权
标题翻译：排气消声器带挡板
公开(公告)号：US08596568B2
公开(公告)日：2013-12-03
申请号：US13094179
申请日：2011-04-26
申请人： Jay M. Francisco , James C. Napier
发明人： Jay M. Francisco , James C. Napier
IPC分类号： B64C1/40 , B64C23/00
CPC分类号： F01D25/30 , B64D33/06 , B64D41/00 , B64D2041/002 , F02K1/827 , F05D2220/50
摘要： An exhaust silencer assembly includes an exhaust duct and an exhaust silencer. The exhaust silencer is disposed about the exhaust duct and has a plurality of solid baffles and at least one perforated baffle The exhaust silencer assembly is disposed downstream of an auxiliary power unit and at least partially attenuates the downstream noise of the combustion gases that result from operation of the auxiliary power unit. In one embodiment, at least one of the plurality of solid baffles is disposed to extend axially between generally radially extending solid baffles, perforated baffle(s), or partially perforated baffles. The axially extending solid baffle allows for cavity depth variation in the silencer to optimize tuning of particular frequencies from the auxiliary power unit.
摘要翻译：排气消声器组件包括排气管和排气消音器。废气消音器设置在排气管周围并且具有多个固体挡板和至少一个穿孔挡板。排气消声器组件设置在辅助动力单元的下游，并且至少部分地衰减由操作产生的燃烧气体的下游噪声的辅助动力单元。在一个实施例中，多个固体挡板中的至少一个设置成在大致径向延伸的固体挡板，多孔挡板或部分穿孔的挡板之间轴向延伸。轴向延伸的固体挡板允许消音器中的腔深度变化以优化来自辅助动力单元的特定频率的调谐。

56. 发明申请

US20120211599A1 FLOW-MODIFYING FORMATION FOR AIRCRAFT WING 审中-公开
标题翻译：飞机改造流程改造
公开(公告)号：US20120211599A1
公开(公告)日：2012-08-23
申请号：US13357024
申请日：2012-01-24
申请人： Romuald MORVANT , Kevin M. BRITCHFORD
发明人： Romuald MORVANT , Kevin M. BRITCHFORD
IPC分类号： B64C23/00
CPC分类号： B64C7/02 , B64C23/06 , Y02T50/162
摘要： An aircraft wing has an engine attachment position at which a gas turbine engine is attached beneath the wing, in use the engine ejecting a propulsive gas jet with a jet shear layer being formed between the gas jet and the surrounding air. The aircraft wing further has one or more elongate, flow-modifying formations protruding from the underside of the wing. The length direction of the or each formation is along the fore and aft direction of the wing with the trailing edge of the formation being rearward of the trailing edge of the wing. The flow-modifying formations can be arranged such that they interact with the jet shear layer to reduce noise generated by the interaction of the jet shear layer and the wing. They can also be arranged to block, attenuate and/or to scatter the noise reflected by the wing.
摘要翻译：飞机机翼具有发动机安装位置，燃气涡轮发动机在该位置附接在机翼下方，在使用中，发动机在气体射流和周围空气之间形成喷射剪切层喷射推进气体射流。飞机机翼还具有从翼的下侧突出的一个或多个细长的，流动改变的构造。这些或每个地层的长度方向是沿着机翼的前后方向，地层的后缘在机翼后缘的后方。流动修饰结构可以被布置成使得它们与喷射剪切层相互作用以减少由喷射剪切层和翼的相互作用产生的噪声。它们还可以被布置成阻挡，衰减和/或散射由机翼反射的噪音。

57. 发明申请

US20120091262A1 FORWARD SWEPT WINGLET 有权
标题翻译：前进开关WINGLET
公开(公告)号：US20120091262A1
公开(公告)日：2012-04-19
申请号：US12905382
申请日：2010-10-15
申请人： Blaine K. RAWDON , John C. VASSBERG
发明人： Blaine K. RAWDON , John C. VASSBERG
IPC分类号： B64C39/10 , B64C23/00
CPC分类号： B64C23/069 , Y02T50/164
摘要： An aircraft may include a pair of wings. A forward swept winglet may be attached proximate to a wing tip of each wing. The forward swept winglet may include a leading edge and a trailing edge. The leading edge of each winglet may extend from the wing at a predetermined forward sweep angle relative to a line perpendicular to a chord of the wing tip in a direction corresponding to a forward portion of the aircraft.
摘要翻译：飞机可能包括一对机翼。向前扫掠的小翼可以附接到每个翼的翼尖附近。向前扫掠的小翼可以包括前缘和后缘。每个小翼的前缘可以相对于垂直于翼尖的翼弦在与飞行器的前部相对应的方向上以预定的前掠角延伸。

58. 发明申请

US20110272529A1 Hamilton H.N2 laminar flow diskette wing 有权
标题翻译：汉密尔顿N.N2层流软磁翼
公开(公告)号：US20110272529A1
公开(公告)日：2011-11-10
申请号：US12932032
申请日：2011-02-16
申请人： Terry Wayne Hamilton
发明人： Terry Wayne Hamilton
IPC分类号： B64C23/00 , B64C3/36 , B64C3/00
CPC分类号： B64C23/005 , Y02T50/166
摘要： A wing assembly has a wing and one or more no-bias laminar flow oval diskettes that are fixed on a support structure along the C/L (center of lift) of an airfoil, of an aircraft wing. The benefit of an oval diskette with laminar flow is that it has no speed limitations and it allows an aircraft to clime at a speed that matches its Ground Effect Lift speed which is a 25% performance increase and a 40% reduction in vortex drag with a increase stability that eliminates inertia coupling of high-speed airfoils.
摘要翻译：机翼组件具有机翼和一个或多个不偏压层流椭圆形软盘，其沿着机翼的翼型的C / L（电梯的中心）固定在支撑结构上。具有层流的椭圆形软盘的好处是它没有速度限制，并且允许飞机以与地面效应提升速度匹配的速度进行搅拌，其速度提高25％，涡流阻力减少40％提高消除高速翼型惯性耦合的稳定性。

59. 发明申请

US20110186689A1 ACTIVE WINGLET 有权
标题翻译：活动WINGLET
公开(公告)号：US20110186689A1
公开(公告)日：2011-08-04
申请号：US13075934
申请日：2011-03-30
申请人： Nicholas R. Guida
发明人： Nicholas R. Guida
IPC分类号： B64C23/00
CPC分类号： B64C23/065 , B64C13/16 , B64C23/076 , Y02T50/164
摘要： An active winglet includes a body portion substantially parallel to a wing of an aircraft, as if it were an extension of the wing. The body portion is attachable to an aircraft wing and includes a controllable airflow modification device coupled thereto. By virtue of having a controllable airflow modification device, the winglet is capable of adjusting a control surface of the controllable airflow modification device in response to in-flight conditions, to reduce wing loads, increase range, and/or increase efficiency.
摘要翻译：活动的小翼包括基本上平行于飞机的翼的主体部分，好像它是机翼的延伸部分。主体部分可附接到飞行器机翼并且包括耦合到其上的可控气流改变装置。由于具有可控气流改变装置，小翼能够响应于飞行中的条件来调节可控气流改变装置的控制表面，以减少机翼载荷，增加范围和/或提高效率。

60. 发明申请

US20110024573A1 EXTENDED WINGLET WITH LOAD BALANCING CHARACTERISTICS 审中-公开
标题翻译：带有负载平衡特性的扩展WINGLET
公开(公告)号：US20110024573A1
公开(公告)日：2011-02-03
申请号：US12774697
申请日：2010-05-05
申请人： Philip S. Kirk , Robert E. Olson
发明人： Philip S. Kirk , Robert E. Olson
IPC分类号： B64C23/00
CPC分类号： B64C23/069 , Y02T50/164
摘要： A winglet and methods of operating an aircraft using the winglet. In some embodiments, the winglet can be mounted to the wingtip of an aircraft and has three segments or portions, namely, a mounting portion, an upwardly extending portion, and a reverse portion, or a portion that extends in an inboard direction.
摘要翻译：小翼和使用小翼操作飞机的方法。在一些实施例中，小翼可以安装到飞行器的翼尖，并且具有三个部分或部分，即安装部分，向上延伸部分和反向部分，或沿内侧方向延伸的部分。

你已经成功收藏专利！

检索式保存成功!

IPRDB

热门服务

关于我们

友情链接

联系方式